GOE 501 AIRFOIL (goe501-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 501 AIRFOIL (goe501-il) Reynolds number: 500,000 Max Cl/Cd: 113.25 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe501-il-500000.txt Download as CSV file: xf-goe501-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 501 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1215 0.10040 0.09790 -0.0897 0.9758 0.0421
-10.500 -0.3536 0.02910 0.02557 -0.1677 0.9430 0.0391
-10.250 -0.3407 0.02663 0.02270 -0.1699 0.9341 0.0399
-10.000 -0.3235 0.02410 0.01994 -0.1713 0.9275 0.0408
-9.750 -0.2989 0.02352 0.01934 -0.1715 0.9225 0.0415
-9.500 -0.2759 0.02306 0.01884 -0.1712 0.9155 0.0424
-9.250 -0.2500 0.02241 0.01810 -0.1715 0.9106 0.0434
-9.000 -0.2277 0.02131 0.01680 -0.1716 0.9039 0.0444
-8.750 -0.2038 0.02025 0.01550 -0.1718 0.8972 0.0455
-8.500 -0.1789 0.01905 0.01403 -0.1722 0.8914 0.0465
-8.250 -0.1555 0.01805 0.01300 -0.1720 0.8833 0.0476
-8.000 -0.1281 0.01750 0.01236 -0.1721 0.8776 0.0485
-7.750 -0.1026 0.01697 0.01175 -0.1720 0.8701 0.0496
-7.500 -0.0757 0.01641 0.01107 -0.1720 0.8641 0.0508
-7.250 -0.0482 0.01595 0.01045 -0.1721 0.8584 0.0521
-7.000 -0.0213 0.01560 0.00996 -0.1719 0.8517 0.0530
-6.750 0.0050 0.01445 0.00868 -0.1721 0.8463 0.0544
-6.500 0.0319 0.01397 0.00818 -0.1721 0.8406 0.0557
-6.250 0.0592 0.01364 0.00781 -0.1720 0.8345 0.0571
-6.000 0.0875 0.01334 0.00740 -0.1721 0.8295 0.0588
-5.750 0.1150 0.01304 0.00702 -0.1720 0.8241 0.0603
-5.500 0.1428 0.01282 0.00672 -0.1719 0.8186 0.0613
-5.250 0.1700 0.01203 0.00585 -0.1720 0.8134 0.0634
-5.000 0.1974 0.01171 0.00552 -0.1719 0.8083 0.0653
-4.750 0.2252 0.01147 0.00526 -0.1719 0.8032 0.0675
-4.500 0.2535 0.01125 0.00497 -0.1719 0.7987 0.0695
-4.250 0.2821 0.01111 0.00474 -0.1719 0.7943 0.0710
-4.000 0.3092 0.01060 0.00423 -0.1719 0.7895 0.0739
-3.750 0.3371 0.01035 0.00397 -0.1719 0.7849 0.0769
-3.500 0.3658 0.01018 0.00374 -0.1719 0.7804 0.0799
-3.250 0.3939 0.01005 0.00357 -0.1719 0.7758 0.0821
-3.000 0.4217 0.00976 0.00329 -0.1718 0.7709 0.0870
-2.750 0.4500 0.00960 0.00310 -0.1718 0.7661 0.0921
-2.500 0.4788 0.00946 0.00295 -0.1719 0.7615 0.1002
-2.250 0.5062 0.00927 0.00288 -0.1718 0.7560 0.1223
-2.000 0.5340 0.00912 0.00282 -0.1717 0.7498 0.1587
-1.750 0.5619 0.00906 0.00276 -0.1715 0.7431 0.1801
-1.500 0.5890 0.00897 0.00271 -0.1712 0.7354 0.1968
-0.750 0.6716 0.00881 0.00265 -0.1707 0.7150 0.2589
-0.500 0.6990 0.00879 0.00267 -0.1705 0.7081 0.2836
-0.250 0.7260 0.00876 0.00269 -0.1702 0.6998 0.3072
0.000 0.7530 0.00877 0.00271 -0.1699 0.6915 0.3287
0.250 0.7796 0.00877 0.00273 -0.1695 0.6815 0.3472
0.500 0.8061 0.00878 0.00276 -0.1691 0.6711 0.3644
0.750 0.8322 0.00881 0.00277 -0.1686 0.6592 0.3807
1.000 0.8574 0.00884 0.00279 -0.1679 0.6435 0.3965
1.250 0.8819 0.00891 0.00282 -0.1671 0.6221 0.4112
1.500 0.9047 0.00903 0.00287 -0.1660 0.5973 0.4282
1.750 0.9273 0.00919 0.00297 -0.1649 0.5743 0.4488
2.000 0.9502 0.00937 0.00312 -0.1639 0.5564 0.4724
2.250 0.9736 0.00953 0.00329 -0.1630 0.5426 0.5034
2.500 0.9969 0.00971 0.00348 -0.1621 0.5310 0.5485
2.750 1.0213 0.00981 0.00368 -0.1614 0.5209 0.6005
3.000 1.0446 0.00989 0.00387 -0.1605 0.5121 0.6627
3.250 1.0674 0.00949 0.00403 -0.1593 0.5039 1.0000
3.500 1.0917 0.00973 0.00420 -0.1586 0.4965 1.0000
3.750 1.1171 0.00990 0.00435 -0.1581 0.4896 1.0000
4.000 1.1412 0.01014 0.00453 -0.1574 0.4828 1.0000
4.250 1.1658 0.01033 0.00470 -0.1567 0.4761 1.0000
4.500 1.1900 0.01052 0.00487 -0.1560 0.4692 1.0000
4.750 1.2132 0.01078 0.00507 -0.1551 0.4630 1.0000
5.000 1.2378 0.01093 0.00525 -0.1545 0.4566 1.0000
5.250 1.2603 0.01116 0.00545 -0.1535 0.4493 1.0000
5.500 1.2830 0.01136 0.00564 -0.1525 0.4416 1.0000
5.750 1.3046 0.01158 0.00585 -0.1513 0.4338 1.0000
6.000 1.3253 0.01181 0.00606 -0.1500 0.4266 1.0000
6.250 1.3450 0.01203 0.00628 -0.1484 0.4175 1.0000
6.500 1.3642 0.01228 0.00652 -0.1468 0.4087 1.0000
6.750 1.3837 0.01254 0.00678 -0.1453 0.4007 1.0000
7.000 1.4030 0.01281 0.00705 -0.1437 0.3924 1.0000
7.250 1.4198 0.01316 0.00736 -0.1418 0.3812 1.0000
7.500 1.4375 0.01349 0.00768 -0.1401 0.3682 1.0000
7.750 1.4534 0.01390 0.00806 -0.1380 0.3530 1.0000
8.000 1.4683 0.01438 0.00849 -0.1359 0.3364 1.0000
8.250 1.4807 0.01499 0.00901 -0.1335 0.3164 1.0000
8.500 1.4907 0.01575 0.00964 -0.1308 0.2877 1.0000
8.750 1.4947 0.01687 0.01055 -0.1273 0.2486 1.0000
9.000 1.4973 0.01816 0.01162 -0.1238 0.2143 1.0000
9.250 1.5058 0.01917 0.01254 -0.1212 0.1994 1.0000
9.500 1.5163 0.02009 0.01343 -0.1190 0.1903 1.0000
9.750 1.5258 0.02109 0.01440 -0.1167 0.1827 1.0000
10.000 1.5382 0.02194 0.01528 -0.1149 0.1771 1.0000
10.250 1.5494 0.02289 0.01624 -0.1129 0.1715 1.0000
10.500 1.5577 0.02405 0.01739 -0.1108 0.1659 1.0000
10.750 1.5722 0.02483 0.01824 -0.1094 0.1611 1.0000
11.000 1.5835 0.02585 0.01929 -0.1077 0.1556 1.0000
11.250 1.5900 0.02724 0.02067 -0.1056 0.1494 1.0000
11.500 1.6070 0.02791 0.02142 -0.1046 0.1431 1.0000
11.750 1.6149 0.02926 0.02275 -0.1029 0.1350 1.0000
12.000 1.6282 0.03024 0.02376 -0.1017 0.1231 1.0000
12.250 1.6330 0.03192 0.02532 -0.0999 0.1015 1.0000
12.500 1.6319 0.03415 0.02743 -0.0978 0.0868 1.0000
12.750 1.6339 0.03622 0.02950 -0.0960 0.0804 1.0000
13.000 1.6336 0.03856 0.03185 -0.0943 0.0752 1.0000
13.250 1.6387 0.04048 0.03383 -0.0930 0.0721 1.0000
13.500 1.6414 0.04270 0.03611 -0.0917 0.0691 1.0000
13.750 1.6415 0.04524 0.03869 -0.0904 0.0662 1.0000
14.000 1.6440 0.04762 0.04114 -0.0894 0.0638 1.0000
14.250 1.6494 0.04975 0.04336 -0.0886 0.0617 1.0000
14.500 1.6516 0.05229 0.04597 -0.0878 0.0592 1.0000
14.750 1.6503 0.05531 0.04902 -0.0871 0.0568 1.0000
15.000 1.6527 0.05798 0.05178 -0.0865 0.0545 1.0000
15.250 1.6574 0.06042 0.05431 -0.0862 0.0520 1.0000
15.500 1.6576 0.06350 0.05744 -0.0859 0.0494 1.0000
15.750 1.6567 0.06682 0.06082 -0.0857 0.0468 1.0000
16.000 1.6608 0.06953 0.06362 -0.0857 0.0435 1.0000
16.250 1.6569 0.07340 0.06751 -0.0859 0.0406 1.0000
16.500 1.6595 0.07644 0.07063 -0.0861 0.0367 1.0000
16.750 1.6555 0.08049 0.07472 -0.0865 0.0337 1.0000
17.000 1.6535 0.08431 0.07860 -0.0870 0.0307 1.0000
17.250 1.6481 0.08869 0.08303 -0.0878 0.0285 1.0000
17.500 1.6447 0.09281 0.08723 -0.0885 0.0267 1.0000
17.750 1.6382 0.09749 0.09196 -0.0896 0.0252 1.0000
18.000 1.6326 0.10208 0.09664 -0.0907 0.0241 1.0000
18.250 1.6288 0.10641 0.10107 -0.0919 0.0231 1.0000
18.500 1.6236 0.11097 0.10572 -0.0932 0.0222 1.0000
18.750 1.6169 0.11585 0.11067 -0.0948 0.0215 1.0000
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